Aerodynamic performance comparison of high power turboprop S-DUCT intake on channel wing at varying Azimuth

Abstract

S-duct intake component for a highly loaded turboprop engine was investigated considering its installation on a channel wing of an active high-lift aircraft using computational fluid dynamics. The objective is to observe the interaction effects of the propeller-nacelle-wing on the S-duct intake aerodynamics, especially when the intake is positioned at different azimuth angles with respect to rotation axis. Single scoop wrap-around type S-duct was integrated into a representative nacelle body. The propeller was modeled as an actuator disc for the slipstream effects. Steady-state Reynolds-averaged Navier-Stokes simulations were run using negative Spalart-Allmaras turbulence model. Although the results showed that the reference S-duct position at φ = 270° had the relatively higher recovery than the other variations, significant improvements in total pressure distortion and intensities were achieved at φ = 0° and 90° positions. Up to 3% decrease in swirl coefficient levels was observed when the wrap-around S-duct was positioned at φ = 90° in comparison to reference position.